Aeroplane



f CDMHHIIQC 244-48 SR FU 8301 UR. 1,638,358

Aus. 9,1927.

H. J. MUNDELL.

AEROPLANE Filed Ang. 18. 1926 2 Sheets-Sheet. 1

I rwentor Attorney 244. AERONAUTICS Aug. 9, 1927. 1,638,358 H. J. MUNDELL AERQPLANE Filed 12.18. 192s 2 sheets-sheet 2 Attorney 244. AERONAUTICS Patented Aug. 9, 1927.

UNITED STATES HERBERT J'. MUNDELL, OF SUMMERVILLE, OREGON'.

.AEROPLANE Application filed August 18, 1926. Serial No. 130,029.

The present invention relates to an aeroplane and has for its prime object to provide a structure which possesses increased efficiency, and a superior capability of maneuvering when in flight as compared with the aeroplanes now in common use.

Another very important object of the invention is to provide an aeroplane with a st-ructure which it eliminates the necessity of providing camber in the wings so that the forward speed of the plane is not decreased.

Another very important object of the invention lies in the provision of an aeroplane of this nature having a fuselage formed in sections so that the nose and tail portions thereof may be disposed at desired angles in relation to the body portion or intermediate portion of the fuselage for the purpose of varying the angle of the planes of the wings to the axes of the nose section and tail section.

Another important object of the invention lies in the provision of novel means for varying the angles of the axis of the propellers in relation to the planes of the wings of the aeroplane.

A still further very important object of the invention lies in the provision of an aeroplane of this nature capable of attaining the objects recited above which possesses an exceedingly simple construction that is thoroughly reliable in operation, one which is inexpensive to manufacture, strong, durable, not likely to easily become out of order, capable of easy adjustment, and otherwise well adapted to the purpose for which it is designed.

With the above and numerous other objects in view as will appear as the description proceeds, the invention resides in certain novel features of construction, and in the combination and arrangement of parts as will be hereinafter more fully described and claimed.

In the drawings Figure 1 is a side elevation of the aeroplane embodying the features of my invention.

Figure 2 is a top plan view thereof.

Figure 3 is a fragmentary longitudinal section through the fuselage thereof.

Figure 4 is a transverse section through the intermediate section of the fuselage.

Referring to the drawings in detail it will be seen that the fuselage of my improved aeroplane is formed in these sections, the central section being indicated by the numeral 5, the tail section by the numeral 6 and the nose section by the numeral 7. The propeller 8 is mounted on the nose section 7 forwardly thereof and co-axially therewith. The nose section 7 is hinged to the bottom 9 of the intermediate section 5 as is indicated at 10, while the tail section 6 is hinged to the rear edge of the bottom 9 of the intermediate section 5 as is indicated at 11. A link plate 12 is hingedly engaged as at 13 with the upper wall of the nose section 7 and as at 14 with the upper wall of the tail section 6. This link plate 12 is preferably provided with a longitudinally extending opening 15 in order that access may be easily had to the interior of the intermediate section 5. The cock pit of the fuselage is preferably disposed in the tail section 6 and is indicated generally by the numeral 16. An instrument board or partition 17 is mounted in the cock pit intermediate the ends ofthe tail section 6 and has journaled therein a shaft 18 the forward end of which is threaded as is indicated at 19 while the rear end, in the cock pit 16, has mounted thereon an operating crank 20. A pair of standards 21 rise from the bottom 9 of the intermediate section 5 and have rockably mounted between their upper ends an internally threaded sleeve 23 with which the threaded end 19 of the shaft 18 is engaged.

The upper wing of the aeroplane is designated by the numeral 24 while the lower wing is designated by the numeral 25. These wings are held in spaced parallel relation by suitable members 26 or in any other preferred manner. It is to be noted that these wings 24 and 25 are not provided with the usual chamber as is the common practice, but extend horizontally when the aeroplane is normally disposed on the ground. The intermediate portion 5 has its bottom 9 fixed to the lower wing 25 in any suitable manner. A truck construction 27 is mounted below the lower wing 25 and has incorporated therein suitable cushioning 28. A drag 30 is pivoted to the rear portion of the tail section 6 as at 31 'and is provided with the shoe 32. The free end of this drag 30 has a rod 33 resiliently connected as at 34 with the tail 6 so as to provide a cushioning effect in landing.

When it is desired to take oif or ascend the shaft 18 is operated to break the sections l ist' 5, 6 and 7 to the dotted line position shown in Figure l, that is, so that the intermedia-te section 5 inclines upwardly and forwardly with the wings while the tail section 6 is disposed substantially horizontal or inclines upwardly and rearwardly while the nose section 7 inclines downwardly and forwardly. Thus the wings are disposed for climbing in the air providing all of the advantages of a camber wing without in any way decreasing the Speed facilities of the aeroplane since the sections,fby the operation ofthe shaft 18, may be brought back into alinement'with each other and that the wings will be disposed in the plane of the iiight to offer the least resistance. Hingedly mounted control sections 36 and 37 are provided in the forward and rear edges respectively of the top wing 24 and are controL. lable through suitable cables 38 lfromY a com-l mon point within thel aeroplane.`

It is thought that the construction, utility, operation, and advantages of this invention will now be clearly understood by those skilled in this art without `a mo-re detailed description thereof. It will be readily apparent that with this 'device the maximum capability of speed and'possibility ofl ma'- neuvering is' attained. This' also provides for economy in operation as will be readily understood. The present embodiment of the invention has been disclosed in detail since in actual practice it attains the features'of advantage enumerated as desirable inthe v statement of the invention and the abo'vede-l scription. It will be apparent'that numerous. changes inthe details of construction, in the combination and arrangement of partsmayl be resorted to wit-hout departure from lthe spirit or scope of the Vinvention. as herein-' aeroplane, a fuselage comprising an inter# mediate portion, a tail portion hingedly mounted at the lower rear portion of the intermediate portion, a nose portion hingedly mounted at the forward bottom portion of the intermediate portion, a link plate hingedly connected with the upper portions of the nose portion and tail portion, and means for .swingingthe tail portion in rela.- tion to the intermediate portion so that the nose portion simultaneously swings therewith.

2. As a new article of manufacture for an aeroplane, a fuselage comprising an intermediate portion, a tail portion hingedly mounted at the lower rear portion of the intermediate portion, a nose portion hingedly mountedl at the forward bottom portion of the intermediate portion, a link plate hingedly connected with the upper portions of the nose portion and tail portion, and meansI for swinging the tail portion in relation to the intermediate portion so that the nose portion simultaneously swings thercwith, said means comprising a pivotally mounted internally threaded sleeve in the intermediate portion, a shaft journaled in the tail portion and th'r-eadedly engaged in the sleeve.

3. As a new article of manufacture for an laeroplane,'a fuselage comprising an intermediate portion, a tail portion hingedly mounted lat the rear, of the intermediate portion, a nose portion hingedly mounted atthefront of the intermediate portion, a link plate hingedly connected with the last two mentioned portions, and means for swinging one ofthe vlast two mentioned portions inrespect to the intermediate portion so that both fof Said last two mentioned portions maybe swung in unison with each other with relation to said intermediate portions,

In ltestimony whereof I aifiX my signature.

HERBERT J. MUNDELL. 

